CN113882904B - Composite blade turbine with unsteady surface layer flow passage - Google Patents
Composite blade turbine with unsteady surface layer flow passage Download PDFInfo
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- CN113882904B CN113882904B CN202111244977.4A CN202111244977A CN113882904B CN 113882904 B CN113882904 B CN 113882904B CN 202111244977 A CN202111244977 A CN 202111244977A CN 113882904 B CN113882904 B CN 113882904B
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- 239000002131 composite material Substances 0.000 title claims abstract description 25
- 239000002344 surface layer Substances 0.000 title claims abstract description 25
- 239000007921 spray Substances 0.000 claims abstract description 18
- 230000005540 biological transmission Effects 0.000 claims abstract description 4
- 239000012530 fluid Substances 0.000 claims description 69
- 239000010410 layer Substances 0.000 claims description 67
- 238000007789 sealing Methods 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 description 20
- 239000007787 solid Substances 0.000 description 12
- 239000000853 adhesive Substances 0.000 description 9
- 230000001070 adhesive effect Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 230000033001 locomotion Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 238000013178 mathematical model Methods 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 230000033764 rhythmic process Effects 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 230000003746 surface roughness Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000004992 fission Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000693 micelle Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Hydraulic Turbines (AREA)
Abstract
The invention belongs to the technical field of turbine equipment, and provides a composite vane turbine with an unsteady surface layer runner, which comprises a rotor assembly, a shell assembly arranged outside the rotor assembly and a power output shaft in transmission connection with the rotor assembly, wherein the rotor assembly comprises: the flywheel, two flywheel relative settings, and be formed with the runner in the opposite one side of two flywheel, the casing subassembly includes: the middle shell is coaxially sleeved on the periphery of the rotor assembly, an annular nozzle chamber is coaxially arranged on the middle shell, a plurality of spray holes are formed in the inner side of the annular nozzle chamber in an annular array, and an air inlet is formed in the outer side of the annular nozzle chamber; and the two cover bodies are respectively arranged at two sides of the middle shell, one opposite side of the two cover bodies is kept sealed with the two inertia wheels, and the two cover bodies are provided with air outlets which are communicated with the flow channel. The composite vane turbine with the unsteady surface layer flow channel has higher power and efficiency and simple structure.
Description
Technical Field
The invention relates to the technical field of turbine equipment, in particular to an unsteady surface layer runner composite vane turbine.
Background
The working principle of impulse turbine (working medium is mainly expanded in jet orifice blade grating) and reaction turbine (working medium is expanded in static blade grating and moving blade grating) is that kinetic energy of working medium (steam or gas) directly impacts turbine rotor blade to obtain reaction force so as to obtain mechanical energy, and the energy conversion efficiency of single-stage turbine can not exceed 45% under special conditions of non-combined cycle and the like by using the working mode, so that energy waste is caused. The power, efficiency and miniaturization of the single-stage turbine cannot be further improved in the technical aspect, and only two ways of obtaining larger power and efficiency under the condition that the working medium input condition is unchanged are needed: one is to use a single stage turbine with larger diameter to increase power and efficiency, and the other is to use a multi-stage turbine to increase power and efficiency, however, both of these approaches make the mechanical structure more and more complex, costly and bulky.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide the composite vane turbine with the unsteady surface layer runner, so as to improve the power and the efficiency of the turbine and have a simple structure.
In order to achieve the above object, the present invention provides a composite vane turbine with an unsteady surface layer runner, comprising a rotor assembly, a housing assembly arranged outside the rotor assembly, and a power output shaft in transmission connection with the rotor assembly, wherein the rotor assembly comprises:
The inertial wheels are oppositely arranged and fixedly connected with each other, and a flow channel is formed on one side of the two opposite inertial wheels;
the housing assembly includes:
the middle shell is coaxially sleeved on the periphery of the rotor assembly, an annular nozzle chamber is coaxially arranged on the middle shell, a plurality of spray holes are formed in the inner side of the annular nozzle chamber in an annular array, and an air inlet is formed in the outer side of the annular nozzle chamber; and
The two covers are respectively arranged on two sides of the middle shell and fixedly connected with the middle shell, one opposite side of each cover is kept sealed with each inertia wheel through a sealing assembly, and the two covers are provided with air outlets which are communicated with the flow channels.
Further, the rotor assembly further comprises an impeller, at least one of which is coaxially arranged between the two inertia wheels;
When the number of the impellers is one, the flow channel is formed between the impellers and the inertia wheel;
When the number of the impellers is greater than or equal to two, the flow passages are formed between the impellers and the inertia wheel and between two adjacent impellers.
Further, the rotor assembly further comprises a plurality of blades, the blades are arranged between the two inertia wheels in an annular array, and two ends of each blade are fixedly connected with the two inertia wheels.
Further, the orifice includes the air inlet section and the section of giving vent to anger that are smooth connection each other, the air inlet section is loudspeaker form and be close to the one end of annular nozzle room is great end, the air inlet section to the come of the working medium fluid in the annular nozzle room is to the slope, the air outlet section is loudspeaker form and keep away from the one end of annular nozzle room and be great end, the air outlet section to rotor assembly's direction of rotation slope.
Further, a plurality of spacing pieces are fixedly arranged in the flow channel, and the plurality of spacing pieces are distributed in a circular array around the rotation center line of the rotor assembly.
Further, the surface of the rotor assembly in contact with the working fluid comprises a number of peaks and/or valleys.
Further, the distance between two adjacent peaks or two adjacent valleys for controlling the roughness of the inner surface of the runner of the rotor assembly is L 1, wherein, L 1 is more than 10mm and equal to or more than 0.01mm.
Further, the thickness of an auxiliary surface layer formed on the surface of the rotor assembly, which is in contact with the working fluid, is delta, the distance between the flow channels is L 2, wherein delta is more than L 2 and is more than or equal to 0.1 delta, and 50mm is more than or equal to 0.1mm.
Further, the flow channel is wavy or planar.
The invention has the beneficial effects that:
The unsteady boundary layer runner composite vane turbine provided by the invention utilizes the boundary layer formed on the solid surface of the runner in the process of flowing fluid in the runner, and utilizes the viscous shear stress of the boundary layer to drive the rotor assembly to rotate, so that the kinetic energy of working fluid is converted into the mechanical energy of the rotor assembly, the power and the conversion efficiency are improved, and the structure is simple.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. Like elements or portions are generally identified by like reference numerals throughout the several figures. In the drawings, elements or portions thereof are not necessarily drawn to scale.
FIG. 1 is a perspective view of a composite vane turbine with an unsteady surface flow path in accordance with one embodiment of the present invention;
FIG. 2 is a front view of the unsteady-surface-layer flowpath composite vane turbine of FIG. 1;
FIG. 3 is a cross-sectional view taken along the direction A-A shown in FIG. 2;
FIG. 4 is a cross-sectional view in the direction B-B shown in FIG. 3;
fig. 5 is an enlarged view at C shown in fig. 3;
FIG. 6 is a perspective view of a rotor assembly of the unsteady-surface-layer flowpath composite vane turbine of FIG. 1;
FIG. 7 is a cross-sectional view as shown in FIG. 6;
fig. 8 is an enlarged view of D shown in fig. 7;
fig. 9 is an enlarged view at E shown in fig. 7;
FIG. 10 is a perspective view of a composite vane turbine with an unsteady surface flow path according to a second embodiment of the present invention;
FIG. 11 is a perspective view of the rotor assembly of the unsteady-surface-layer flowpath composite vane turbine of FIG. 10;
FIG. 12 is a cross-sectional view of the device shown in FIG. 11;
FIG. 13 is a perspective view of a composite vane turbine with an unsteady surface flow path according to a third embodiment of the present invention;
FIG. 14 is a perspective view of the rotor assembly of the unsteady-surface-layer flowpath composite vane turbine of FIG. 13;
FIG. 15 is a cross-sectional view as shown in FIG. 14;
FIG. 16 is a perspective view of a composite vane turbine with an unsteady surface flow path in accordance with a third embodiment of the present invention;
FIG. 17 is a perspective view of the rotor assembly of the unsteady-surface-layer flowpath composite vane turbine of FIG. 16;
fig. 18 is a cross-sectional view of fig. 17.
Reference numerals:
100-rotor assembly, 110-flywheel, 120-impeller, 130-blade, 140-spacer, 101-runner, 102-air outlet, 103-first blade positioning slot, 200-housing assembly, 210-intermediate housing, 211-annular nozzle chamber, 212-jet orifice, 213-air inlet, 220-cover, 221-air outlet, 222-mounting slot, 201-air inlet section, 202-air outlet section, 300-power output shaft, 400-seal assembly, 410-seal ring, 420-seal spring.
Detailed Description
Embodiments of the technical scheme of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present invention, and thus are merely examples, and are not intended to limit the scope of the present invention.
It is noted that unless otherwise indicated, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs.
In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present application.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. In the description of the present invention, the meaning of "plurality" is two or more unless specifically defined otherwise.
In the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected or detachably connected or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present application, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
As shown in fig. 1-18, the present invention provides an unsteady-surface-layer-runner composite vane turbine, comprising a rotor assembly 100, a housing assembly 200 disposed outside the rotor assembly 100, and a power take-off shaft 300 drivingly connected to the rotor assembly 100.
Wherein the rotor assembly 100 includes an inertia wheel 110. Specifically, the number of the inertia wheels 110 is two, the two inertia wheels 110 are disposed opposite to each other and fixedly connected to each other, and the flow channel 101 is formed on opposite sides of the two inertia wheels 110. Specifically, the two inertia wheels 110 are positioned by the power output shaft 300 and are fixedly connected by bolts, and the two inertia wheels 110 are spaced apart from each other by a certain distance, thereby forming the flow path 101 between the two inertia wheels 110. Of course, the flywheel 110 is further provided with a plurality of air outlet holes 102 communicating with the flow channel 101 along the axis line thereof, and the plurality of air outlet holes 102 are arranged on the flywheel 110 in a circular array around the axis line of the flywheel 110. When in use, working fluid enters the flow channel 101, an adhesive surface layer is formed on the solid surface of the rotor assembly 100 contacted with the working fluid, and the fluid rotates with the rotor assembly 100 under the action of adhesive shearing stress of the adhesive surface layer, so that energy conversion is performed in the flow channel 101 to improve the conversion efficiency.
The housing assembly 200 includes a middle housing 210 and a cover 220.
The middle housing 210 is annular and coaxially sleeved on the periphery of the rotor assembly 100, an annular nozzle chamber 211 is coaxially formed on the middle housing 210, a plurality of spray holes 212 are formed on the inner side of the annular nozzle chamber 211 in an annular array, and an air inlet 213 is formed on the outer side of the annular nozzle chamber. By providing the annular nozzle chamber 211 on the middle housing 210, all the spray holes 212 can uniformly intake air, so that the arrangement of the air intake pipe is reduced, and the structure is simple. Meanwhile, the plurality of spray holes 212 are arranged in a circular array, so that working fluid can uniformly enter the flow channel 101 and form torque in the same direction of the flow channel 101, and the conversion efficiency is improved.
The number of the covers 220 is two, and the two covers 220 are respectively disposed at two sides of the middle housing 210 and fixedly connected with the middle housing 210. Specifically, the cover 220 is fixedly coupled with the middle case 210 through a coupling bolt through a sealing assembly and maintains a seal. The opposite sides of the two covers 220 and the two inertia wheels 110 are kept sealed by the sealing assembly 400, and the two covers 220 are provided with air outlets 221, and the air outlets 221 are communicated with the flow channel 101.
Specifically, the power take-off shaft 300 is drivingly connected to the rotor assembly 100 by splines, while being rotatably connected to the two covers 220 by bearings.
Specifically, the seal assembly 400 includes a seal ring 410 and a seal spring 420. Wherein, a side of the cover 220 facing the flywheel 110 or a side of the flywheel facing the cover is coaxially provided with a mounting groove 222, and the sealing ring 410 is slidably mounted in the mounting groove 222. The number of the seal springs 420 is plural, the plurality of seal springs 420 are disposed in the mounting groove 222 in a circular ring array, both ends of the seal springs are in contact with the seal ring 410 and the mounting groove 222, and the seal springs 420 have a tendency to move the seal ring 410 in a direction approaching the flywheel 110 or the cover 220 in a natural state. Specifically, when the mounting groove 222 is opened on the cover 220, the seal spring 420 has a tendency to move the seal ring 410 in a direction approaching the flywheel; when the mounting groove is formed in the flywheel 110, the seal spring 420 tends to move the seal ring 410 in a direction approaching the cover 220.
When in use, the working fluid sprayed from the spray holes 212 flows into the flow channel 101, and in the process of flowing in the flow channel 101, an adhesive surface layer is formed on the solid surface of the rotor assembly 100 contacted with the working fluid, and under the action of the viscous shear stress of the adhesive surface layer, the fluid drives the rotor assembly 100 to rotate, so that energy conversion is performed in the flow channel 101.
Specifically, the fluid is a general term of gas and liquid in nature, and is a medium with continuous fluidity, and the fluid with actual viscosity is also called newtonian fluid. This is because the fluid is composed of a large number of molecules, and relative movement is very easy to occur between the molecules in each part inside, and the intensity of the movement between the molecules changes with the physical conditions such as the speed, pressure and temperature of the fluid. When two adjacent layers of fluid relatively slide or shear deform, shear stress preventing the fluid from relatively sliding or shearing deform is generated in opposite directions due to the interaction between fluid molecules, and is called viscous shear stress. According to experiments, the viscosity shear stress is related to physical environments such as viscosity coefficients, relative sliding speeds and temperatures of different fluids.
Thus, if the working fluid (steam or gas) contacts the solid surface at high reynolds numbers and there is relative motion, the thin fluid layer near the solid surface reduces the velocity of the working fluid due to viscous shear stress; the fluid closely attached to the solid surface is adhered to the object plane, and the relative speed between the fluid and the object plane is equal to zero; the solid surface in the flow field presents a very thin shear layer, i.e., an interfacial layer. The flow outside the boundary layer can be essentially considered to be a non-viscous ideal fluid, the flow rate being the main flow zone velocity. While fluid molecules next to the solid surface are adsorbed on the object plane with a flow velocity of zero. Thus, there must be a region of very large normal velocity gradient near the solid surface, which is the boundary layer.
Because the viscous shear stress and the inertia force in the boundary layer are of the same order of magnitude, compared with a conventional turbine which relies on the fluid energy of a working medium (steam or gas) to impact the blade, the fluid energy of the working medium (steam or gas) can transmit more kinetic energy to the rotor assembly through the boundary layer, so that the utilization efficiency of the fluid energy of the turbine is improved, the output power is improved, the vibration phenomenon of the rotor assembly is reduced, and the turbine works stably.
Meanwhile, according to the flow state of the working fluid, the boundary layer is divided into a laminar boundary layer and a turbulent boundary layer, and the two boundary layers have different layered flows (generally divided into an inner layer and an outer layer). The inner layer comprises an adhesive bottom layer close to the wall surface, the inner layer accounts for about 20% of the whole layer of the boundary layer, the adhesive shear stress is maximum, and the inner layer consists of a plurality of small eddies; the buffer layer is arranged upwards, and the turbulence layer is arranged upwards until the outer layer of the boundary layer is a momentum exchange larger turbulence layer consisting of large-size vortex. The outer layer is from this turbulent layer up to where the velocity is very similar to the outflow. For rotor assemblies, it is primarily the turbulent boundary layer that is active in their actual operation.
When the fluid with high Reynolds number is converted into mechanical work through the rotor assembly, the fluid flow in the rotor assembly is changed from the laminar flow boundary layer to the turbulent flow boundary layer, and the viscous shear stress of the turbulent flow boundary layer is far greater than that of the laminar flow boundary layer, so that the turbulent kinetic energy transmission in the turbulent flow boundary layer is also greater. This is because turbulence energy is generated by strong shear at the bottom of the turbulent boundary layer, i.e. at the transition layer of the inner layer. Inside the turbulent boundary layer, the turbulent energy is gradually transferred from inside to outside, and the small vortex is transferred to the large vortex, so that the mixing of the high-turbulent energy fluid and the low-turbulent energy fluid is formed. The mixing happens continuously inside the whole boundary layer, the turbulence pulsation and the differential turbulence between the random movements of fluid molecules are random, unsteady and three-dimensional, rotational flow, and a mimicking structure exists behind the random turbulence. Turbulent pulsations continue to grow, break up and dissipate turbulent micelles and the fission of eddies form the transfer of energy. Especially when the fluid Reynolds number is improved and the roughness of the solid wall surface is larger, the granularity of the flow structure in the turbulent boundary layer is smaller, the shearing effect is stronger, and the transmitted kinetic energy is larger and more efficient.
Therefore, the conversion of fluid energy of working medium (steam or gas) by utilizing the physical characteristics of the turbulent flow unsteady surface layer is far more efficient than the mode that kinetic energy of fluid energy of working medium (steam or gas) directly impacts turbine blades to obtain rotary mechanical work in the prior art, and the rotary mechanical power generation device has the advantages of high power, high efficiency, smaller and quieter vibration of a rotor assembly, simple structure and better economical efficiency.
Regarding the macrostructure of the three-dimensional unsteady turbulent boundary layer within the rotor assembly, it may be expressed using the following mathematical model:
speed profile: u +＝U/v*,y+＝yv*/v,
Where u + is the dimensionless speed and y + is the dimensionless distance.
In particular, velocity in an adhesive underlayerThe linear change is carried out along with y, so the linear bottom layer (u +＝y+) is also called; the transition layer is the transition from the viscous underlayer to the fully turbulent layer, and the molecular viscous shear stress is as important as the turbulent shear stress (u +≈-3.05+5ln y+); the flow of the logarithmic rhythm layer is in a complete turbulence state, and the molecular viscosity stress can be ignoredWherein k=0.40, b=5.5); wake rhythms layer: the flow is still complete turbulence, but the turbulence intensity is obviously weakened, the speed gradient is very small, and the molecular viscosity influence is weakened; an adhesive top layer: the transition from the boundary turbulent layer to the external non-turbulent layer causes the external non-turbulent layer to be involved in the boundary layer and mixed, so that the turbulent intensity is continuously weakened, and the speed is influenced by the external non-turbulent layer.
Wherein,
Wherein delta is the boundary layer thickness.
It should be noted that, the three-dimensional unsteady turbulence boundary layer mathematical model in the rotor assembly is simply an expression of the turbulence boundary layer macroscopic structure in the flow channel 101, but the boundary layer structure is complex in reality and cannot be accurately solved by the turbulence mathematical model, so that the data cannot be used to limit the protection scope of the present invention.
In one embodiment, the rotor assembly 100 further includes an impeller 120, at least one impeller 120 being coaxially disposed between the two inertia wheels 110. Specifically, the impeller 120 and the flywheel 110 are coupled as one body by a coupling bolt.
When the number of impellers 120 is one, a flow passage 101 is formed between the impellers 120 and the flywheel 110, that is, two flow passages 101 are formed in the rotor assembly 100.
When the number of the impellers 120 is greater than or equal to two, the impellers 120 are sequentially disposed between the two impellers 110 at intervals, and the flow passages 101 are formed between the impellers 120 and the impellers 110 and between the adjacent two impellers 120, that is, not less than three flow passages 101 are formed on the rotor assembly 100. Of course, the impeller is also provided with an air outlet 102.
The purpose of increasing the number of flow channels 101 is achieved by providing an impeller 120 between two inertia wheels 110. By increasing the number of the flow channels 101, the number of boundary layers formed in the rotor assembly 100 is increased, that is, the contact area between the working fluid and the rotor assembly 100 is increased, so that more working fluid can be converted into energy through the boundary layers formed on the surface of the rotor assembly 100, the purpose of obtaining higher high turbulence energy is achieved, and the conversion efficiency is further improved.
In one embodiment, rotor assembly 100 further includes blades 130. The number of the blades 130 is plural, the plurality of blades 130 are disposed between the two inertia wheels 110 in a ring array, and two ends of the blades are fixedly connected with the two inertia wheels 110 respectively. Specifically, the opposite sides of the two flywheel 110 are provided with the first vane positioning slots 103 matched with the vanes 130, the vanes 130 are fixedly clamped between the two flywheel 110 through the first vane positioning slots 103, and when the working fluid is sprayed from the spray holes 212, the working fluid impacts the vanes 130, so that kinetic energy of the working fluid is converted into mechanical energy of the vanes 130 to drive the vanes 130 to rotate, and the whole rotor assembly 100 is driven to rotate. When the blade 130 needs to be replaced or repaired, the blade 130 which needs to be replaced or repaired can be taken out by removing one flywheel 110, so that the replacement and repair of the blade 130 are facilitated, meanwhile, as the blade 130 is a single independent part, when the blade 130 needs to be replaced or repaired, only the damaged blade 130 needs to be repaired, and the repair cost is low.
When the impeller 120 is disposed between the two inertia wheels 110, the impeller 120 may be located at the inner sides of the blades 130 and fixedly connected with the inertia wheels 110, so as to achieve the purpose of carrying the impeller 120 to rotate together, or a second blade positioning groove may be formed on the impeller 120, and the impeller 120 is clamped with the blades 130 through the second blade positioning groove, so as to achieve the purpose that the blades 110 drive the impeller 120 to rotate.
In use, the working fluid ejected from the nozzle 212 first impacts the blade 130, thereby converting the kinetic energy of the working fluid into mechanical energy for rotation of the rotor assembly 100 to increase the instantaneous torque during turbine start-up to increase the kinetic energy for turbine start-up, so as to facilitate start-up to reduce energy loss during start-up, and further improve energy conversion efficiency.
In one embodiment, the nozzle 212 includes an inlet section 201 and an outlet section 202 that are smoothly connected to each other. The air inlet section 201 is horn-shaped, and one end, close to the annular nozzle chamber 211, is a larger end, and the air inlet section 201 inclines towards the direction of the working fluid in the annular nozzle chamber 211. When in use, working fluid enters the annular nozzle chamber 211 from the air inlet 213 of the annular nozzle chamber 211, and in the process of flowing in the annular nozzle chamber 211, the working fluid can enter the spray hole 212 along the inlet of the air inlet section 201 of the spray hole 212, so that the resistance of air entering the spray hole 212 from the annular nozzle chamber 211 is reduced, the energy loss is reduced, and the energy conversion efficiency is further improved. And the air inlet section 201 of the spray hole 212 is arranged in a horn shape, so that the speed of working fluid sprayed out of the spray hole 212 can be improved by increasing the air inflow of the spray hole 212.
The gas outlet section 202 is flared and the end remote from the annular nozzle chamber 211 is the larger end, the gas outlet section 202 being inclined in the direction of rotation of the rotor assembly 100. By arranging the air outlet section 202 of the spray hole 212 in a horn shape, the working fluid sprayed from the spray hole 212 is dispersed, so that the working fluid can impact the blade 130 in the maximum range, and the energy conversion efficiency is improved. By arranging the gas outlet section 202 of the nozzle 212 to be inclined to the rotation direction of the rotor assembly 100, the working fluid ejected from the nozzle 212 is facilitated to impact the vane 130 to drive the rotor assembly 100 to rotate.
In one embodiment, a plurality of spacers 140 are fixedly disposed in the flow channel 101, and the plurality of spacers 140 are distributed in a circular array around the rotation center line of the rotor assembly 100.
Through fixedly arranging the spacing pieces 140 in the flow channel 101 to control the distance between the flow channels 101, the spacing pieces 140 can also play a role in supporting the impeller 120 and/or the flywheel 110, stabilize the flow of working fluid, reduce the vibration of the rotor assembly 100, and further improve the energy conversion efficiency.
In one embodiment, the surface of rotor assembly 100 that contacts the working fluid includes a number of peaks and/or valleys. Specifically, the surfaces of the blades 130, the impeller 120, and the flywheel 110 that are in contact with the working fluid are each roughened surfaces composed of many small peaks and valleys. Because the fluid in the boundary layer contacts with the solid surface and has relative motion, if the solid surface has a rough surface formed by a plurality of tiny peaks and valleys, viscous shear stress can be increased in the process of energy exchange with the fluid, so that the energy conversion efficiency is improved.
By increasing the surface roughness within the flow channels of the rotor assembly 100, viscous shear forces of the working fluid on the rotor assembly 100 are increased, thereby improving energy conversion efficiency.
In one embodiment, the distance between two adjacent peaks or two adjacent valleys for controlling the roughness of the inner surface of the rotor assembly flow channel is L 1, wherein 10mm > L 1. Gtoreq.0.01 mm. By controlling the surface roughness in the flow channel of the rotor assembly 100, the purpose of controlling the viscous shear stress of the boundary layer is achieved, and the energy conversion efficiency is improved.
In one embodiment, the boundary layer formed on the surface of the rotor assembly 100 in contact with the working fluid has a thickness delta, and the flow channels 101 have a spacing L 2, wherein delta > L 2 is greater than or equal to 0.1 delta, and 50mm > delta is greater than or equal to 0.1mm. By controlling the distance between the flow channels 101 and the thickness of the boundary layer, more working fluid forms the boundary layer on the surface of the rotor assembly 100, so that the kinetic energy of the working fluid is converted into mechanical energy of the rotor assembly 100 through the boundary layer.
In one embodiment, the flow channel 101 is wavy or planar in shape. Specifically, when the surface of the flow channel 101 is wavy, the surfaces of the impeller 120 and the flywheel 110 constituting the flow channel 101 are wavy; and when the flow passage 101 is planar, the surfaces of the impeller 120 and the flywheel 110 constituting the flow passage 101 are planar. Preferably, the flow channel 101 is in a wavy shape, and the flow channel 101 is in a wavy shape, so that the energy conversion efficiency can be improved by increasing the acting time of the working fluid on the rotor assembly 100, and the contact area between the fluid and the rotor assembly 100 can be increased under the condition that the radius of the rotor assembly 100 is the same, so that the energy conversion efficiency can be improved.
In one embodiment, the number of vanes is equal to the number of orifices. Specifically, each blade corresponds to one spray hole, and the impact thrust of working fluid to the blade is improved by arranging a plurality of spray holes, so that the energy conversion efficiency is improved.
In the description of the present invention, numerous specific details are set forth. However, it is understood that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention, and are intended to be included within the scope of the appended claims and description.
Claims (7)
1. The utility model provides a unsteady boundary layer runner composite vane type turbine, includes rotor subassembly, sets up the casing subassembly of rotor subassembly outside and with the power take off shaft of rotor subassembly transmission connection, its characterized in that: the rotor assembly includes:
The inertial wheels are oppositely arranged and fixedly connected with each other, and a flow channel is formed on one side of the two opposite inertial wheels;
the housing assembly includes:
the middle shell is coaxially sleeved on the periphery of the rotor assembly, an annular nozzle chamber is coaxially arranged on the middle shell, a plurality of spray holes are formed in the inner side of the annular nozzle chamber in an annular array, and an air inlet is formed in the outer side of the annular nozzle chamber; and
The two cover bodies are respectively arranged at two sides of the middle shell and fixedly connected with the middle shell, one opposite side of each cover body and each inertia wheel are kept sealed through a sealing assembly, and the two cover bodies are provided with air outlets which are communicated with the flow channels;
the rotor assembly further comprises an impeller, at least one impeller being coaxially arranged between two of the inertia wheels;
When the number of the impellers is one, the flow channel is formed between the impellers and the inertia wheel;
When the number of the impellers is greater than or equal to two, the flow passages are formed between the impellers and the inertia wheel and between two adjacent impellers;
The rotor assembly further comprises a plurality of blades which are arranged between the two inertia wheels in an annular array, two ends of each blade are fixedly connected with the two inertia wheels, and the impeller is located on the inner side of each blade.
2. The unsteady surface layer flow channel composite vane turbine as described in claim 1, further comprising: the jet orifice comprises an air inlet section and an air outlet section which are smoothly connected with each other, the air inlet section is in a horn shape and is close to the larger end at one end of the annular nozzle chamber, the air inlet section inclines towards the direction of working fluid in the annular nozzle chamber, the air outlet section is in a horn shape and is far away from the larger end at one end of the annular nozzle chamber, and the air outlet section inclines towards the rotating direction of the rotor assembly.
3. The unsteady surface layer flow channel composite vane turbine as claimed in any one of claims 1 or 2, characterized by: the flow channel is internally and fixedly provided with a plurality of spacing pieces, and the plurality of spacing pieces are distributed in a circular array around the rotation center line of the rotor assembly.
4. The unsteady surface layer flow channel composite vane turbine as described in claim 1, further comprising: the roughened surface of the rotor assembly in contact with the working fluid includes a plurality of peaks and/or valleys.
5. The unsteady surface layer runner composite vane turbine as described in claim 4, further comprising: the distance between two adjacent peaks or two adjacent valleys for controlling the roughness of the inner surface of the runner of the rotor assembly is L 1, wherein, the distance between 10mm and L 1 is more than or equal to 0.01mm.
6. The unsteady surface layer flow channel composite vane turbine as described in claim 5, further comprising: the thickness of an auxiliary surface layer formed on the surface of the rotor assembly, which is contacted with working fluid, is delta, the distance between the flow channels is L 2, wherein delta is more than L 2 and is more than or equal to 0.1 delta, and 50mm is more than or equal to 0.1mm.
7. The unsteady surface layer flow channel composite vane turbine as described in claim 6, further comprising: the flow passage is wavy or planar.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102182517A (en) * | 2011-05-04 | 2011-09-14 | 南京航空航天大学 | Boundary layer turbine with blade plate |
| CN109983202A (en) * | 2015-06-10 | 2019-07-05 | 绿青蛙涡轮机(英国)有限公司 | Boundary layer turbines, corresponding rotor assembly and partition |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5217348A (en) * | 1992-09-24 | 1993-06-08 | United Technologies Corporation | Turbine vane assembly with integrally cast cooling fluid nozzle |
| AUPQ446299A0 (en) * | 1999-12-02 | 2000-01-06 | Collins, Ralph | Micromachines |
| CN112253266A (en) * | 2020-09-25 | 2021-01-22 | 深圳朴坂科技有限公司 | Bladeless turbine and automatic adjusting method for disc body distance thereof |
| CN112160943A (en) * | 2020-10-13 | 2021-01-01 | 中国人民解放军海军工程大学 | Anti-surge structure of compressor casing of gas turbine and surge margin evaluation method thereof |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102182517A (en) * | 2011-05-04 | 2011-09-14 | 南京航空航天大学 | Boundary layer turbine with blade plate |
| CN109983202A (en) * | 2015-06-10 | 2019-07-05 | 绿青蛙涡轮机(英国)有限公司 | Boundary layer turbines, corresponding rotor assembly and partition |
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